Systems and Methods for Launching Munitions

ABSTRACT

Systems and methods for launching munitions are provided. In some embodiments, the system may include a cover for use with a munitions launcher including a housing with a face. The cover may include a lid, a defined passage through the lid, and an actuator. The lid may be configured to mount to the face of the munitions launcher. The defined passage through the lid may be sized to allow a munition to pass through the lid when launched by the launcher and to substantially cover any other munitions disposed at least partially within the munitions launcher. The actuator may be configured to operate the lid in a manner that moves the defined passage in relation to the face of the munitions launcher. Movement of the defined passage in relation to the face of the munitions launcher may uncover at least one munition that was substantially covered prior to the movement of the defined passage and substantially cover any other munitions disposed at least partially within the munitions launcher.

TECHNICAL FIELD

The present disclosure relates to munitions, and in particular, systemsand methods for launching munitions.

BACKGROUND

Munitions such as air to ground missiles (AGM), air to air missiles(AMM), and rockets can be carried and launched from various vehicletypes including aircraft vehicles (e.g., fighter jets, helicopters,unmanned air vehicles (UAVs)), land vehicles (e.g., tanks, BMPs), and/orwatercraft (e.g., aircraft carrier, submarines, other surface craftand/or undersea craft). Launchers, fixed to the vehicle, may be used tosecure the munitions during transportation as well as used to deploy themunitions. Conventional munition launchers include a rail or tubestructure for holding the munitions and electromechanical apparatus forfixing the munitions to the launcher. A release mechanism arms themunitions and releases it for launching. For example, the launcher mayinclude power supply equipment that controls the fusing and firing ofthe munitions.

The next generation of munitions may include further developments intarget viewing, seeking, and/or detection (e.g., smart rockets).Individual munitions with target viewing, seeking, and/or detectionfeatures may require improvements in launcher technology, includingchanges in the rail structure, electromechanical apparatus for fixingthe munitions to the launcher, and/or the release mechanism. In otherapplications, munitions and their respective launchers may be usedwithout an associated vehicle, instead being adapted for transportationby an individual and/or alternative forms of transportation.

SUMMARY

The present disclosure provides techniques for launching munitions thatsubstantially eliminates or reduces at least some of the disadvantagesand problems associated with previous methods and systems.

In some embodiments, the system may include a cover for use with amunitions launcher including a housing with a face. The cover mayinclude a lid, a defined passage through the lid, and an actuator. Thelid may be configured to mount to the face of the munitions launcher.The defined passage through the lid may be sized to allow a munition topass through the lid when launched by the launcher and to substantiallycover any other munitions disposed at least partially within themunitions launcher. The actuator may be configured to operate the lid ina manner that moves the defined passage in relation to the face of themunitions launcher. Movement of the defined passage in relation to theface of the munitions launcher may uncover at least one munition thatwas substantially covered prior to the movement of the defined passageand substantially cover any other munitions disposed at least partiallywithin the munitions launcher.

In other embodiments, a launcher configured to retain a munition duringtransport by a vehicle is provided. The launcher may comprise a housing,at least two tubes, circuitry, a lid with a defined passage, and anactuator. The housing may have a face through which munitions pass whenlaunched. The at least two tubes may be disposed at least partiallywithin the housing and configured to hold munitions for transportation.The circuitry may provide electrical communication with munitionspresent within the at least two tubes. The lid may be configured tomount to the face of the munitions launcher. The defined passage throughthe lid may be sized to allow a munition launched from a first tube topass through the lid when launched by the launcher and to substantiallycover any other munitions disposed in a second tube. The actuator may beconfigured to operate the lid in a manner that moves the defined passagein relation to the face of the munitions launcher. Movement of thedefined passage in relation to the face of the munitions launcher mayuncover a munition held in the second tube and substantially cover thefirst tube.

In some embodiments, a method for launching a munition from a launchercoupled to a vehicle is provided. The system may include a housing,couplings, tubes, a lid, a defined passage through the lid, and anactuator. The housing may have a face through which munitions pass whenlaunched. The housing may be coupled to a vehicle and configured toretain at least two munitions during transport by the vehicle. Thecouplings may provide mechanical connection between the vehicle and thehousing and electrical connectivity between the vehicle and the housing.The couplings may be configured to route electrical signals from thevehicle to the at least two munitions. The tubes may be disposed atleast partially within the housing and configured to hold the at leasttwo munitions for transportation. The lid may be configured to mount tothe face of the housing. The defined passage through the lid may besized to allow a munition launched from a first tube to pass through thelid when launched by the launcher and to substantially cover any othermunitions disposed in a second tube. The actuator may be configured tooperate the lid in a manner that moves the defined passage in relationto the face of the housing. Movement of the defined passage in relationto the face of the munitions launcher may uncovers a munition held inthe second tube and substantially cover the first tube.

The systems and methods of the present disclosure may provide animproved system for launching munitions capable of target viewing,seeking, and/or detection (e.g., smart rockets). For example, incontrast to known systems, the teachings of the present disclosure mayprotect sensors associated with a guidance and control unit housed inthe nose of a munition. In known systems, the nose of a munition may beexposed to the exhaust plume of a neighboring munition once launched.The systems and methods of the present disclosure may provide improvedperformance and/or reliability of munitions, including associatedelectronic circuitry, sensors, and/or guidance and control functions.Other technical advantages will be readily apparent to one skilled inthe art from the following figures, descriptions, and claims. Moreover,while specific advantages have been enumerated above, variousembodiments may include all, some or none of the enumerated advantages.

BRIEF DESCRIPTION OF THE DRAWINGS

A more complete understanding of the present embodiments and advantagesthereof may be acquired by referring to the following description takenin conjunction with the accompanying drawings, in which like referencenumbers indicate like features, and wherein:

FIG. 1A illustrates an aircraft vehicle with an example launchertransporting munitions, in accordance the teachings of the presentdisclosure;

FIG. 1B illustrates the launcher of FIG. 1A, in accordance with theteachings of the present disclosure;

FIG. 2 illustrates an example munition that may be launching inaccordance with the teachings of the present disclosure;

FIG. 3 shows the launcher of FIG. 1A during a launch of a munition, inaccordance with one embodiment of the present disclosure;

FIG. 4 illustrates an example launcher incorporating the teachings ofthe present disclosure; and

FIGS. 5A and 5B show the launcher of FIG. 4 during successive launchesof munitions, in accordance with the teachings of the presentdisclosure.

DETAILED DESCRIPTION

Preferred embodiments and their advantages are best understood byreference to FIGS. 1 through 5B, wherein like numbers are used toindicate like and corresponding parts.

FIG. 1A illustrates an example vehicle 1 that includes an examplelauncher 2, 110 in accordance with teachings of the present disclosure.Vehicle 1 may be an aircraft vehicle such as a helicopter, an unmannedaerial system (UAS), fighter jets (e.g., F-16, F/A-18, etc.) and/orother aircraft vehicles configured to transport and launch munitions.While FIG. 1 illustrates an aircraft vehicle, other vehicles are alsocontemplated. For example, vehicle 1 may be a land vehicle (e.g.,tankers, transporter erector launchers, and/or military vehicles), awatercraft vehicle (e.g., submarines, surface ships, etc.) or othersuitable vehicle.

Launcher 2 coupled to vehicle 1 may be configured to house munitions 20(see FIG. 2) during transport. In some embodiments, launcher 2 mayinclude electrical contacts through couplings 12 providing electricalcommunication between each of munitions 20 and a user (e.g., pilot ofvehicle 1, mission control in communication with vehicle 1, etc.). Insome embodiments, during deployment of vehicle 1, a user (e.g., a pilotof vehicle 1 or mission control remotely located from vehicle 1 and incommunication with vehicle 1) may launch munitions 20 by communicatingwith munitions 20 via the electrical communication provided by launcher2. The communication may include signals defining the coordinateinformation of a specific target and/or other information that allowsmunitions 20 to accurately strike the target, reducing or substantiallyeliminating incidental or collateral damage.

FIG. 1B illustrates launcher 2 of FIG. 1A in more detail. In someembodiments, launcher 2 may include housing 10, couplings 12, and tubes14. Launcher 2 may be configured to secure munitions 20 duringtransportation (e.g., during flight and/or ground travel) and providecontinuous electrical communication to munitions 20 until time oflaunch, in accordance with certain embodiments of the presentdisclosure. Launcher 2 may be configured to house munitions 20 in tubes14. Launcher 2 may also include optional housing 10 configured toenclose various electrical components that couple with munitions 20 aswell as munitions 20. It is noted that launcher 2 shown in FIG. 1B is anexample. Other suitable types of apparatuses or system configured tolaunch a munition will be understood by persons having ordinary skill inthe art.

Housing 10 may include any device, component, and/or features oflauncher 2 configured to enclose various components of launcher 2 andcouple to vehicle 1. Housing 10 may be integrally formed as a part oflauncher 2 or may be secured to launcher 2. In some embodiments, housing10 may enclose one or more electrical components disposed therein andmay route the appropriate electrical components to each munition 20 inhousing 10.

Housing 10 may include one or more electrical transmission wires orcables and/or any other transmission component configured to provide acommunication channel between a user (e.g., a pilot or mission controlin communication with vehicle 1) and munition 20. In some embodiments,electrical components of housing 10 may transmit signals sent from auser to one or more munitions 20, where the signals provide detailsabout a launching including, for example, GPS coordinates of a target,launch time, etc.

Couplings 12 may include any component, device, and/or feature oflauncher 2 and/or housing 10 configured to attach launcher 2 to vehicle1. Couplings 12 may include electrical connections between vehicle 1 andlauncher 2 and/or munitions 20. For example, in some embodiments,couplings 12 may include both mechanical attachment points andelectrical connectors. Couplings 12 may be configured to mate withmatching and/or corresponding features of vehicle 1, depending on thetype of vehicle 1 in use.

Couplings 12 may include one or more conductors that provide electricalcommunication between vehicle 1 and munition 20. Couplings 12 mayinclude electrical adaptor or interface configured to connect electricalcomponents of vehicle 1 to launcher 2. In some embodiments, couplings 12may include small computer system interface (SCSI), male or femaleelectrical connectors, and/or other adaptors and/or interfaces.

Tubes 14 may include any component, device, and/or feature of launcher 2and/or housing 10 configured for use with munitions 20. For example,tubes 14 may provide a housing for individual munitions 20, includingprotection from physical impact, contact, and/or contamination duringstorage, transport, and/or launching of neighboring munitions 20. Tubes14 may be arranged within launcher 2 and/or housing 10 in variousstacking patterns. As shown in FIGS. 1A and 1B, in the exampleembodiment, housing 10 provides 19 tubes 14 for munitions 20.

FIG. 2 illustrates an example munition 20, in accordance with theteachings of the present disclosure. Munition 20 may be aprecision-guided munition (PGs), smart bomb, smart weapon, guided bombunit (GBU), guided missile (e.g., laser guided missile, infrared guidedmissile, etc.), smart rocket, and/or other weapon that may includeelectronics. Munition 20, as directed by commands sent via electricalcomponents by the pilot or mission control in communication with vehicle1, may be configured to precisely hit a specific target with greaterreliability and/or accuracy which may, in turn, reduce collateraldamage.

Munition 20 may include a nose 22, a body 26, and a propulsion unit 28.Although one particular embodiment is shown in FIG. 2, persons havingordinary skill in the art will be able to apply the teachings of thepresent disclosure to a variety of munitions as described above.

In some embodiments of munition 20, nose 22 may house electroniccomponents (e.g., sensors) configured to view, search for, and/or detecttargets as part of a guidance and control (G&C) unit of munition 20. Forexample, G&C may include a signal processing unit, a global positioningsystem (GPS), an inertial measurement units (IMUs) configured to provideneeded inertial guidance to the munitions, imaging system, and/or othercomponents. One or more of the components of the G&C unit of munition 20may be used to precisely guide munition 20 during launch and/or afterlaunch. In other embodiments, the G&C unit may be used to track, view,and/or identify potential targets for munition 20 prior to launch.

Nose 22 may include one or more sensitive electronics components subjectto compromised performance when dirty, obscured, and/or impacted. Insome embodiments, nose 22 may include a leading surface 24. Leadingsurface 24 may include different materials than the rest of nose 22,those materials selected to be transparent to one or more sensors innose 22. For example, leading surface 24 may be transparent to infraredsensors, thermal sensors, visible light, etc.

Body 26 may include any component, device, and/or feature of munition 20configured to provide structure and/or housing for the variouscomponents, including a G&C unit, nose 22, and/or propulsion unit 28. Insome embodiments, munition 20 may have a roughly cylindrical shape. Forexample, body 26 may include a metal cylinder housing propellant for useby propulsion unit 28, electrical conductors for communication between aG&C unit and various components of launcher 2 and/or vehicle 1.

Propulsion unit 28 may include any component, device, and/or feature ofmunition 20 configured to provide thrust to munition 20 for launching.For example, propulsion unit 28 may include a jet engine, a rocket,and/or other forms of propulsion (e.g., chemical rockets,solid-propellant rockets, liquid-propellant rockets, hybrid rockets,and/or thermal rockets). Some embodiments may include a chemical rocketgenerating thrust by the combustion of rocket propellant. Someembodiments may generate thrust by expelling propellants that exitpropulsion unit 28 at great velocity. The exit of propellant frompropulsion unit 28 through exhaust 30 may create an exhaust plume 32.Exhaust plume 32 may include flame, combustion products, noise, unburnedpropellant, etc.

Referring to FIG. 3, a view of launcher 2 and munitions 20 a and 20 b isshown, with portions of housing 10 removed, in accordance with certainembodiments of the present disclosure. Munition 20 a, secured inlauncher 2, and specifically in tube 14 of launcher 2, may be incontinuous contact with vehicle 1 and/or mission control in contact withvehicle 1. The electrical signals communicated between vehicle 1 andmunition 20 a may include, for example, GPS coordinates of a target,launch time, and/or other mission-specific information regarding theintended target.

At time of launch, after appropriate signals and/or other informationare sent to munition 20, launcher 2 may launch munition 20. As shown inFIG. 3, munition 20 a may exit tube 14 of launcher 2. Launching munition20 a may include igniting propellant in propulsion unit 28 a andgenerating exhaust plume 32 a. During the launch of munition 20 a,various components of a G&C unit in nose 22 a may gather informationand/or data through leading surface 24 a of nose 22 a. As leadingsurface 24 a of nose 22 a always remains ahead of exhaust plume 32 a,the materials and/or energy of exhaust plume 32 a is unlikely to impingeon leading surface 24 a of nose 22 a of munition 20 a.

In contrast, however, the leading surface 24 b of munition 20 b may beexposed to exhaust plume 32 a as munition 20 a exits housing 10 oflauncher 2. Exhaust plume 32 a may deposit dirt, film, unspentpropellant, combustion products, and/or heat on leading surface 24 b ofnose 22 b of munition 20 b, as well as any other munitions 20. Thecontents and/or force of the propellant exiting exhaust 30 a maydetrimentally impact the performance and/or operation of munition 20 band/or other remaining munitions 20.

FIG. 4 illustrates an example launcher 40 with a rotating munitionscover 50 incorporating the teachings of the present disclosure. Launcher40 may include housing 42 and cover 50. Housing 42 may include anycomponents, devices, and/or features as described in relation to housing10, including couplings 44, and tubes 46. As shown in FIG. 4, however,tubes 46 in launcher 40 may be arrayed around a centerline 48 at amatching radius, R. In other respects tubes 46 may include anycomponents, devices, and/or features as described in relation to tubes14. In the embodiment shown, launcher 40 may include twelve tubes 46arrayed near the perimeter of a face 43 of a generally cylindricalhousing 42. Such an array of tubes 46 may allow the use of rotatingcover 50 as shown in FIG. 4. FIGS. 5A and 5B show launcher 40 duringsuccessive launches of munitions 20, in accordance with the teachings ofthe present disclosure.

Cover 50 may include any device, component, and/or feature of launcher40 configured to define a passage for a munition 20 as it is launchedand, at the same time, protect one or more other munitions 20 mounted inlauncher 40. For example, cover 50 may include a flat panel generallymatching the shape of face 43 of housing 42. Cover 50 may include a hole52 generally configured to match the shape of tube 46. For example, hole52 may be a circular opening in cover 50 with a diameter similar to thediameter of a cylindrical tube 46. Although substantially round tubes 46and hole 52 may be depicted, any shape or configuration may be used asmay be appropriate depending on the form and function of munition 20.Hole 52 may also be configured to allow a G&C unit housed in nose 22 ofmunition 20 to view, seek, and/or detect a target prior to its launchfrom launcher 40.

Cover 50 may be mounted to housing 42 by any device, component, and/orfeature of launcher 40 configured to move cover 50 as necessary todefine a passage for the various tubes 46 of launcher 40. For example,as shown in FIGS. 5A and 5B, cover 50 may rotate around centerline 48 tomove hole 52 to reveal various tubes 46 and, thereby, define successivepassages for various munitions 20. Cover 50 may provide protection tomunitions 20, and specifically leading surface 24 of nose 22 of munition20. As shown in FIGS. 5A and 5B, the use of cover 50 during the launchof munition 20 a may no longer subject the leading surface 24 b to theexhaust plume 32 a of munition 20 a.

In one example embodiment, cover 50 may be mounted to launcher 40 bymeans of an actuator 54 mounted along centerline 48 of housing 42.Actuator 54 may include a rotating motor mounted between the array oftubes 46 in launcher 40. In some embodiments, cover 50 may be mounted tothe rotor of an electric motor 54 controlled by the operation ofelectronic logic and/or circuitry associated with the firing mechanismof launcher 40 and/or munitions 20. In some embodiments, cover 50 may bemounted to housing 40 around the perimeter of face 43 using anappropriate bearing rather than at centerline 48. In some embodiments,cover 50 may be configured to cover a single tube 46 and be individuallyoperated (e.g., one cover per tube).

Although the figures and embodiments disclosed herein have beendescribed with respect to information handling systems, it should beunderstood that various changes, substitutions and alternations can bemade herein without departing from the spirit and scope of thedisclosure as illustrated by the following claims.

What is claimed:
 1. A cover for use with a munitions launcher includinga housing with a face, the cover comprising: a lid configured to mountto the face of the munitions launcher; a defined passage through thelid, the passage sized to allow a munition to pass through the lid whenlaunched by the launcher and to substantially cover any other munitionsdisposed at least partially within the munitions launcher; and aactuator configured to operate the lid in a manner that moves thedefined passage in relation to the face of the munitions launcher;wherein movement of the defined passage in relation to the face of themunitions launcher uncovers at least one munition that was substantiallycovered prior to the movement of the defined passage and substantiallycovers any other munitions disposed at least partially within themunitions launcher.
 2. A cover according to claim 1, wherein the lidincludes a plate having a substantially equivalent shape of the face ofthe housing of the munitions launcher.
 3. A cover according to claim 1,wherein the defined passage includes a hole passing through the lid, thehole having a diameter substantially equivalent to a diameter of a tubein the housing of the munitions launcher.
 4. A cover according to claim1, further comprising the lid mounted to a rotor of a motor.
 5. A coveraccording to claim 1, further comprising the lid mounted to a perimeterof the face of the housing of the munitions launcher.
 6. A launcher forlaunching munitions, the launcher comprising: a housing having a facethrough which munitions pass when launched; at least two tubes disposedat least partially within the housing, the at least two tubes configuredto hold munitions for transportation; circuitry providing electricalcommunication with munitions present within the at least two tubes; alid configured to mount to the face of the munitions launcher; a definedpassage through the lid, the passage sized to allow a munition launchedfrom a first tube to pass through the lid when launched by the launcherand to substantially cover any other munitions disposed in a secondtube; and an actuator configured to operate the lid in a manner thatmoves the defined passage in relation to the face of the munitionslauncher; wherein movement of the defined passage in relation to theface of the munitions launcher uncovers a munition held in the secondtube and substantially covers the first tube.
 7. A launcher according toclaim 6, further comprising the launcher configured to mount to avehicle.
 8. A launcher according to claim 6, further comprising thelauncher configured to mount to a vehicle and wherein the vehiclecomprises an aircraft vehicle, a land vehicle, or a watercraft vehicle.9. A launcher according to claim 6, wherein the munition is aprecision-guided munition (PGM), a smart bomb, a smart weapon, a guidedbomb unit (GBU), a guided missile or a smart rocket.
 10. A launcheraccording to claim 6, wherein the lid includes a plate having a shapesubstantially equivalent to a shape of the face of the housing of themunitions launcher.
 11. A launcher according to claim 6, wherein thedefined passage includes a hole passing through the lid, the hole havinga diameter substantially equivalent to a diameter of the at least twotubes.
 12. A launcher according to claim 6, further comprising the lidmounted to a rotor of a motor.
 13. A launcher according to claim 6,further comprising the lid mounted to a perimeter of the face of thehousing of the munitions launcher.
 14. A system for launching munitionsfrom a vehicle, the system comprising: a housing having a face throughwhich munitions pass when launched; the housing coupled to a vehicle andconfigured to retain at least two munitions during transport by thevehicle; couplings providing mechanical connection between the vehicleand the housing and electrical connectivity between the vehicle and thehousing; the couplings configured to route electrical signals from thevehicle to the at least two munitions; tubes disposed at least partiallywithin the housing, the tubes configured to hold the at least twomunitions for transportation; a lid configured to mount to the face ofthe housing; a defined passage through the lid, the passage sized toallow a munition launched from a first tube to pass through the lid whenlaunched by the launcher and to substantially cover any other munitionsdisposed in a second tube; and an actuator configured to operate the lidin a manner that moves the defined passage in relation to the face ofthe housing; wherein movement of the defined passage in relation to theface of the munitions launcher uncovers a munition held in the secondtube and substantially covers the first tube.
 15. A system according toclaim 14, wherein the vehicle comprises an aircraft vehicle, a landvehicle, or a watercraft vehicle.
 16. A system according to claim 14,wherein the munition is a precision-guided munition (PGM), a smart bomb,a smart weapon, a guided bomb unit (GBU), a guided missile or a smartrocket.